XFOIL Version 6.94 Calculated polar for: NACA 63,3-418 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3341 0.01218 0.00569 -0.0739 0.6415 0.6309 0.500 0.3916 0.01224 0.00575 -0.0742 0.6320 0.6413 1.000 0.4492 0.01241 0.00597 -0.0747 0.6235 0.6512 1.500 0.5077 0.01250 0.00604 -0.0754 0.6134 0.6608 2.000 0.5645 0.01253 0.00615 -0.0756 0.6045 0.6724 2.500 0.6220 0.01287 0.00650 -0.0761 0.5949 0.6833 3.000 0.6793 0.01291 0.00661 -0.0766 0.5848 0.6935 3.500 0.7355 0.01298 0.00677 -0.0767 0.5753 0.7043 4.000 0.7929 0.01339 0.00720 -0.0771 0.5642 0.7169 4.500 0.8478 0.01342 0.00741 -0.0771 0.5546 0.7283 5.000 0.9034 0.01346 0.00751 -0.0770 0.5419 0.7402 5.500 0.9593 0.01372 0.00779 -0.0772 0.5287 0.7523 6.000 1.0110 0.01356 0.00780 -0.0763 0.5097 0.7646 6.500 1.0641 0.01375 0.00805 -0.0759 0.4914 0.7789 7.000 1.1135 0.01388 0.00826 -0.0747 0.4711 0.7928 7.500 1.1625 0.01411 0.00861 -0.0738 0.4460 0.8071 8.000 1.2051 0.01453 0.00906 -0.0717 0.4120 0.8228 8.500 1.2394 0.01530 0.00979 -0.0685 0.3647 0.8403 9.000 1.2567 0.01669 0.01099 -0.0630 0.3055 0.8611 9.500 1.2572 0.01897 0.01306 -0.0562 0.2445 0.8879 10.500 1.2515 0.02596 0.01967 -0.0474 0.1422 1.0000 11.000 1.2518 0.03076 0.02425 -0.0456 0.1066 1.0000 11.500 1.2524 0.03563 0.02902 -0.0440 0.0853 1.0000 12.000 1.2591 0.04005 0.03347 -0.0428 0.0724 1.0000 12.500 1.2610 0.04515 0.03867 -0.0416 0.0630 1.0000 13.000 1.2665 0.05012 0.04371 -0.0410 0.0570 1.0000 13.500 1.2607 0.05619 0.04984 -0.0399 0.0510 1.0000 14.000 1.2745 0.06060 0.05442 -0.0397 0.0487 1.0000 14.500 1.2842 0.06559 0.05954 -0.0397 0.0454 1.0000 15.000 1.2930 0.07080 0.06484 -0.0401 0.0424 1.0000 15.500 1.2947 0.07608 0.07023 -0.0389 0.0382 1.0000 16.000 1.3047 0.08150 0.07585 -0.0401 0.0369 1.0000 16.500 1.3108 0.08722 0.08178 -0.0412 0.0345 1.0000 17.000 1.3138 0.09353 0.08826 -0.0426 0.0323 1.0000 17.500 1.3161 0.10004 0.09492 -0.0443 0.0305 1.0000 18.000 1.3153 0.10707 0.10208 -0.0466 0.0288 1.0000 18.500 1.3003 0.11560 0.11093 -0.0483 0.0266 1.0000 19.000 1.2939 0.12428 0.11988 -0.0527 0.0260 1.0000 19.500 1.2878 0.13327 0.12909 -0.0579 0.0245 1.0000 20.000 1.2734 0.14364 0.13974 -0.0639 0.0234 1.0000 20.500 1.2488 0.15581 0.15225 -0.0718 0.0227 1.0000 21.000 1.2296 0.16817 0.16484 -0.0802 0.0212 1.0000